Erik Lapkhanov
@itm.dp.ua
Department of system analysis and control problems
Institute of technical mechanics of National academy of science of Ukraine and State space agency of Ukraine
EDUCATION
1) National Aerospace University “Kharkov aviation institute” – Bachelor’s Degree. Specialty: Automation and Computer-Integrated Technologies. Qualification: Technical expert in physical sciences and technology. Diploma with Honour (2010 -2014).
2) National Aerospace University “Kharkov aviation institute” – Master’s Degree. Specialty: Automation and Computer-Integrated Technologies. Qualification: Research engineer in automation and computer-integrated technologies, computing systems designer. Diploma with Honour (2014-2016).
3) Oles Honchar Dnipro National University, Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine (dual education) – Ph. D. in automation and instrumentation. Specialty: Automation and Computer-Integrated Technologies (Dynamics, ballistics and spacecraft control). (2016-2021)
RESEARCH INTERESTS
Dynamics, ballistics and spacecraft control
Automation and instrumentation, applied mathematics, control systems
Scopus Publications
Scholar Citations
Scholar h-index
Scholar i10-index
Scopus Publications
Anatoliy Alpatov, Mykola Dron’, Aleksandr Golubek, and Erik Lapkhanov
Springer Science and Business Media LLC
Dmytro Kabachenko and Erik Lapkhanov
Private Company Technology Center
Evaluating the effectiveness of the implementation of an investment project is a key issue when making management decisions both at the stage of setting up a startup and for expanding an existing business. This paper reports a systematic approach to building a mathematical model to solve the task of forecasting the effectiveness of business projects, taking into account the influence of factors of the external economic environment. Proposed factors include the impact of supply and demand on the price of goods, political and industry risks, the volume of commodity supply and sales. In view of this, a method for calculating the political component of the discount coefficient using the Fourier series has been proposed. Using the theory of differential equations, correlation and regression analysis, a mathematical model for forecasting indicators of efficiency of business project implementation taking into account the influence of factors of the external economic environment has been constructed. Based on it, a generalized algorithm for applying a mathematical model to predict the effectiveness of investment projects in various business sectors has been developed. The results from applying differential equations and variable discount coefficient showed a decrease in NPV by 14 %, and PI by 5.1 %, due to more accurate consideration of the political component in calculating the discount factor. Also, with the influence of supply and demand on the price of goods and nonlinear cash flows, it was found that the payback period does not clearly indicate the effectiveness of the implementation of an investment business project. Determining these factors provides more accurate information to the investor or business owner when forecasting the stability of a business project for making management decisions on its implementation
Petro Zheliabov and Erik Lapkhanov
OU Scientific Route
The spacecraft controllability of the angular motion is possible only with operability of the attitude and orbit control system (AOCS) of the spacecraft, sensors, actuators and the spacecraft power system. However, there is a rather significant probability of failure of this equipment during the operation of the spacecraft. This is especially observed after half of the spacecraft's lifetime or because of emergency situations. There is a problem which is connected with providing the maximum performance of the AOCS in case of partial failures of their actuators (reaction wheels (RW), magnetorquer rods (MGTR), etc.).
 Thus, the purpose of this work is the development and synthesis of special algorithms for spacecraft angular motion control in the emergency situations which are connected with RWs partial failures and restrictions of onboard electricity consumption. The approach of synthesis of this control algorithms is based on using mobile control methods which allow to reserve RWs by MGTRs. There are different variants of control loops depending on MGTRs turning on combinations. There were proposed two types of control switching functions: time-periodic and switching by deviation. Also was proposed a methodology of controller synthesis using these switching functions.
 Using this methodology and computer simulation, it was shown the possibility of providing angular nadir orientation and stabilization of the spacecraft with maximum 1−1.5 deg error in case of time-periodic switching functions implementation. Switching by deviation allows to reduce onboard electricity consumption for 25−30 % comparing with using time-periodic switching. However, the accuracy of stabilization significantly lower in case of switching by deviation. Considering these estimates, the corresponding methodological recommendations were formulated for use switching functions depending on emergency
S. Khoroshylov and E. Lapkhanov
National Academy of Sciences of Ukraine (Co. LTD Ukrinformnauka) (Publications)
Introduction. Electromagnetic actuators are widely used in spacecraft (SC) attitude control systems. These actuators can be modified by using slewing permanent magnets (ASPM) as sources of torque instead of electromagnets. These modified devices consume less onboard electricity for SC attitude control than the conventional ones.Problem Statement. An algorithm for attitude stabilization of a SC using ASPM was proposed in previous studies, where the pole placement technique and pulse-width modulation (PWM) were used to design the controller. However, this approach does not allow the designers to find optimal values of the required magnetic torques, which may result in frequent engagement of the stepper motors of the ASPMs and their significant energy consumption. This controller has such a drawback because its gains are selected without taking into account time-periodic properties of the Earth magnetic field.Purpose. The purpose of the study is to design the algorithm for the SC angular stabilization by the ASPMs taking into account time-periodic properties of the Earth magnetic field.Materials and Methods. The solution of the time-periodic Riccati equation was used for the controller design. Mathematical modeling and computer simulation of SC motion was applied to build the model of the plan and validate the results.Results. A time-periodic based SC attitude control algorithm has been designed. Taking into consideration the time-periodic properties of the magnetic field of Earth allow us to optimize the required magnetic control torques. This algorithm minimizes the frequency of the actuation of the ASPM sashes, and thus reduces onboard energy consumption.Conclusions. The designed algorithm increases the control efficiency of SC attitude control by using jointly the ASPMs, time-periodic linear-quadratic regulator and pulse-width modulator.
А. Алпатов, О. Кузнецов, О. Палій, and Е. Лапханов
National Academy of Sciences of Ukraine (Co. LTD Ukrinformnauka) (Publications)
Вступ. Зростання інтересу до освоєння космічного простору та нові технології супутникової навігації та зв’язку призвели до збільшення кількості космічних апаратів (КА) на навколоземних орбітах і створення орбітальних угрупувань. На сьогодні головним засобом, що здійснює виведення КА на навколоземні орбіти, є ракети-носії, відпрацьовані верхні ступені яких, після виведення КА, залишаються на навколоземних орбітах і уворюють космічне сміття (КС).Проблематика. Проблема зростання кількості КС є однією із ключових у сучасній космонавтиці. Значне накопичення фрагментів КС на деяких кластерах орбіт може чинити значні перешкоди діючим КА, а також призвести до глобальних проблем — ефекту Кеслера. Одним із джерел зростання КС є відпрацьовані верхні ступені ракет-носіїв (РН). Розробка засобів відведення верхніх ступенів РН з навколоземних орбіт є актуальною, а проєкт РН легко класу «Циклон-1М» розробки ДП «КБ «Південне» ім. М. К. Янгеля» є однією з перспективних розробок.Мета. Розробка науково-технічного забезпечення модернізації аеродинамічної системи відведення для використання на верхньому ступені ракети-носія «Циклон-1М».Матеріали й методи дослідження. Застосовано методи прикладної механіки, математичного й комп’ютерного моделювання руху космічних апаратів.Результати. Розроблено науково-технічне забезпечення для створення нової аеродинамічної системи відведення (АСВ) верхнього ступеня РН «Циклон-1М». Створено нову конструкцію аеродинамічного елементу АСВ у формі трьох ортогонально розміщених круглих дисків, що дозволяє підвищити ефективність застосування АСВ. Запропоновано конструктивну схему та технологію виготовлення контейнера для зберігання АСВ на верхньому ступені РН «Циклон-1М» з використанням сотових технологій, що дозволяє мінімізувати масу системи.Висновки. Технічний результат запропонованої розробки демонструє збільшення ефективності застосування АСВ при неорієнтованому кутовому русі під час відведення РН та дозволяє зменшити масу системи зберігання.
Erik Lapkhanov, Oleksandr Palii, and Aleksandr Golubek
Private Company Technology Center
This paper reports a study into the influence exerted by the thermal flows of space environment on the deformation of the shell of a space inflatable platform with a payload. The mathematical model of the effect of temperature fluctuations on the mass-inertial characteristics of the space inflatable platform of an ellipsoidal shape has been improved. The following assumptions were introduced to the model. The temperature distribution on the illuminated part and the unlit part of the shell is uniform. The gradient of the temperature difference between the illuminated and unlit parts is the same for all points of the shell. To determine deformations, a moment-free theory was used. The model of the space inflatable platform is a «rubber bullet» that works only for stretching and compression. All deformations are elastic. The advantages and limitations of the use of the developed mathematical model have been determined. Computer simulation of the orbital motion of a space inflatable platform with a payload in a sun-synchronous orbit was carried out. The material of the platform shell is Kapton. Estimates of temperature fluctuations in the illuminated and unlit part of the shell and the temperature of the gas inside it were obtained. The dependence of elastic deformations on temperature was determined, taking into account the Young’s modulus of the material. The influence of changes in gas pressure on the movement of payload attachment points and the change in the inertia tensor have been determined. The obtained results showed that the inertia tensor varies within the order of 10–5 kgm2. The maximum deviation of the fastening points of the payload from the initial position on the illuminated part of the shell was about 10–6 m. Considering the stability of the structure to the effects of heat flows of the space environment, the possibility of using space inflatable platforms as a means for separating a grouping of satellites has been shown
А. Алпатов, Е. Лапханов, and О. Палій
National Academy of Sciences of Ukraine (Co. LTD Ukrinformnauka) (Publications)
Вступ. Для стабілізації середовища космічного сміття відпрацьовані космічні апарати та верхні ступені ракет-носіїв необхідно відводити з орбіти.Проблематика. Проведений аналіз надувних аеродинамічних систем відведення космічних апаратів з орбіти показав, що вони є ефективним засобом відведення космічних апаратів з орбіти на висотах до 800 км, однак мають певні недоліки: ймовірність пошкодження фрагментами космічного сміття через чутливість матеріалу оболонки, а також ймовірність електростатичного пробою.Мета. Розробка конструктивної схеми та вибір параметрів аеродинамічної системи відведення космічних апаратів, розроблених ДП «КБ «Південне», з орбіти.Матеріали й методи. Методи механіки космічного польоту, математичне моделювання задач проєктування.Результати. Розрахунки показали, що час відведення космічного апарату «Січ-2-1» із планованої орбіти складає близько 6,5 років при масі аеродинамічної системи відведення 9 кг, що складає 5% від маси зазначеного космічного апарата. Визначено, що у разі збільшення часу відведення космічного апарата «Січ-2-1» з планованої орбіти після завершення експлуатації до 25 років, масу аеродинамічної системи можна зменшити до 4,5 кг. При масі аеродинамічної системи відведення в 9 кг, межею ефективного застосування зазначеної аеродинамічної системи відведення є висоти від 730 до 750 км на близьких до кругових орбітах різної дислокації і висоти не більше 700 км в перигеї та 842 км в апогеї на малоеліптичних орбітах.Висновки. Виходячи із вимог ДП КБ «Південне» до масових і габаритних параметрів засобу відведення, було розроблено конструктивну схему і проєктний вигляд аеродинамічної системи відведення, що розгортається. Особливістю конструкції є компактність, що забезпечується застосуванням пружинних механізмів і маловитратних мікроелектродвигунів, що розгортають аеродинамічні елементи. Така конструкція займає незначний об’єм на космічному апараті «Січ-2-1»
Petr Zheliabov, Erik Lapkhanov, Dmytro Faizullin, Anatoliy Kulabukhov, and Koju Hiraki
Praise Worthy Prize
Anatolii Alpatov, Serhii Khoroshylov, and Erik Lapkhanov
Private Company Technology Center
It is known that the synthesis of the relevant control law is performed and appropriate control devices are selected for specific tasks of controlling relative spacecraft motion. Flywheels, control moment gyroscopes, electromagnetic devices with permanent magnets and micro-jet engines are used as actuators in controlling the orientation and stabilizing the spacecraft. For example, flywheel motors together with electromagnets are most often used to ensure precise spacecraft stabilization in remote Earth monitoring (REM) problems. At the same time, there is a series of problems pertaining to the control over the relative motion of spacecraft where there is no need for precise spacecraft stabilization and ensuring minimal errors in orientation. These problems may include spacecraft orientation for charging solar batteries or orientation control for research and meteorological spacecraft. The study's purpose is to synthesize a law for spacecraft orientation control algorithm when using executive devices with permanent magnets (EDPM). EDPMs are the devices controlling spacecraft orientation. They consist of rotary permanent magnets, stepper motors, and capsule-screens with shutter flaps. Opening and closure of the capsule-screen flaps and rotation of permanent magnets in a certain way ensure the generation of a discrete control magnetic moment. It should be noted that EDPMs do not provide accurate spacecraft stabilization and hence they are not suitable for the REM purpose. However, EDPMs consume less on-board energy than other spacecraft orientation control systems and are useful in problems requiring less accurate stabilization. A control law was synthesized for controlling spacecraft equipped with EDPM using a nonlinear controller and a pulse-width modulator. Areas of effective EDPM application for various space-related problems including orientation and stabilization of aerodynamic elements perpendicular to the dynamic flow of the incoming atmosphere were determined. Advantages of using EDPMs in comparison with electromagnetic executive devices in the problems pertaining aerodynamic element stabilization in aerodynamic systems of deorbiting worked-out spacecraft from low Earth orbits were shown.
Erik Lapkhanov and Serhii Khoroshylov
Private Company Technology Center
The study has considered the possibility of creating an aeromagnetic system for removing space debris from low Earth orbits. The peculiarity of the design of the aeromagnetic deorbiting system is the use of magnetic controls for the relative position of the aerodynamic element with permanent rotary magnets that are shielded with the help of special screen capsules with shutters. It should be noted that this system is offered for aerodynamically unstable spacecraft. Besides, to analyse the performance and benefits of using permanent magnet aeromagnetic input systems, a corresponding discrete law is proposed to control the magnetic parts. The control of the relative position of the aerodynamic element in the orbital coordinate system is carried out in order to orient and stabilize it perpendicular to the dynamic incident atmospheric flow. A mathematical simulation has been performed for the orbital motion of a spacecraft during its removal with the help of a permanent magnet aeromagnetic system from different orbits. It has been determined that when stabilizing the aerodynamic element perpendicular to the vector of the incident dynamic atmospheric flow, the withdrawal time is reduced by 25 % compared with the non-oriented passive deorbiting. However, this advantage during the removal time is peculiar only to aerodynamic elements whose midsection area is much larger than a quarter of the total surface area. It is noteworthy that the design of aeromagnetic evacuation systems is only appropriate using aerodynamically deployable sail elements and is not effective at all for large inflatable elements. Thus, the development of an aeromagnetic space debris removal system with permanent magnet controls extends the boundaries of effective use of aerodynamic sailing systems. The use of permanent magnet units provides a new direction for further research on the orientation of large-scale space systems with minimal fuel and onboard energy consumption